Airplane



Dec, 2, I S.'-HART ET AL I AIRPLANE Filed May 17 1920 3 Sheets-Sheet 1Elmo/MM SETH HAM- Rosem- I. EusTIs Clues/M4 9 Dec. 1924- 1,517,289 s.HART ET AL AIRPLANE F led May 17 1920 s Sheets-Sheet 2 814mm darn HAHTRosem- I, EUS'TJS Dec. 2,1924. I v 1,517,289

I s. HART ET AL AIRPLANE Filed y .17 1920 3 Sheets-Sheet 5 awumtoz 65THHnnr 62X): Rosam- I.Eus'r15 earn HART Ann 'nonnga'r I. nus'rrs, or LOSANGELES, camronm.

- I AIRPLANE.

Application filled May 17, 1920. Serial No. 381,867.

To all whom it may concern:

Be it known that we, SETH HART and ROBERT I. EUSTIS, citizens of theUnited States, residin at Los'Angetes, county of tate of California,have in- Los Angeles, vented certain new and useful Improvements, inAirplanes, of .which the following is a specification.

ThlS invention relates to improvements in airplanes. It has moreparticularly to do with the control of the propelling means.

The objects of the invention are:

- First, to propeller w ereby the angle of the propeller blades can becontrolled and the propeller regulated in its action while the machineis flying.

Second, to provide such an adjustable propeller in which the blades canbe reversed by the pilot. I

Third, to provide direct connection means from the cockpit of anairplane to control the propeller and regulate the angle of the blades,either. for varying the action of the propeller or for reversing thesame.

Fourth, to provide im roved control means for an airplane in lighting orlanding.

Further objects and objects relating to details and economies ofconstruction and operation will definitely appear from the detaileddescription to follow.

We accomplish the objectsof our invention by the devices and meansdescribed 'in the following specification. The invention is clearlydefined and pointed out in the claims.

A structure which is a preferred embodiment of our invention is fullyillustrated in the accompanying drawing, forming apart of thisspecification, in'which:

Fig. I is a detail perspective view of our invention adapted and appliedto. a Curtis JrNH airplane.

Fig. II is an enlarged detail plan view of the front end of the engine,the propeller hub and the connecting means for our improvements, aportion of the propeller blades being broken away. 1

Fig. III is an enlarged detail transverse elevation view, partially insection, on line 3-3 of Figs. II and VII, showing details of theadjusting means for varying the angle of the propeller blades while themachine is in flight.

- Fig. is an enlarged detail transverse rovide an effectively controlledII and III, showing details of the yoke connection, the outer portion ofthe propeller blades being broken away.

Fig. V is an enlarged elevation view of the control lever and segmentand ofthe throttle control as it would appear from r the inside of thecockpit.

Fig. VI is an enlarged detail view of the improved latch and notchedsegment portion whereby very fine adjustment is secured. v

Fig. VII is a detail longitudinal sectional view through the hub sleeveand inner end of the propeller blade, showing a sleeve and arrows at theends of the section lines and --similar numerals of reference refer toslmilar parts throughout the several views.

Considering the numbered parts of the drawing, the numeral 1 indicatesgenerally the improved propeller means, 2 is the fu selage of anairplane, 3 istheradiator, 4 is the front end of the engine, .5 is thehub of the propeller secured to the propeller shaft 5'. .6, 6 arethepropeller blade sleeves preferably made integral with the hub 5. Thepropeller blades 7 are. of the usual constructio'n, being somewhatmodified to make them reversible. The inner ends of the ropeller bladesare supported in thrust bal or roller bearings, 8 and 9, as seen in Fig.VII, as it is desirableto minimize the friction to facilitate themanipulation. Friction is occasioned'by the heavy centrifugal'pull onsectional view taken on line of Figs. v

theblades. A vertical pin 10 is inserted through the shank of eachpropeller blade and when in the vertical position the propeller bladesare at neutral.

We show the details of the right hand propeller blade. whichof course isidentical with the-other blade when it is swung to the same position, asthe two parts are precisely symmetrical. Therefore the descriptionof Ione of these devices is sufiicient' for both.

Th'epin 10 is connected by a, link 11 through itspivot 12 to he yoke orring bearing 13 having a bracket 14thereon to which the link llispivoted at 15. 1A; yoke 16 is secured'to the inner .end of the hub andis disposed. transversely" to the pro- 'peller' hub sleeves.- Pins 17extend therefrom to bosses 18 above and below the center of the hub andthe sliding yoke or ring 13 is slidably disposed on these pins or rods17 so that the same maybe moved readily back andforth thereon. Thebearing yoke 20 embraces the revolving ring 13, there being a suitablethrust ball bearing between the same, not necessary. to be shown here,as our invention does not pertain to the detail of the bearing. v

To this bearing yoke is secured'a pair of pins 21 (see Figs. II, III andIV) which arecarried by the brackets 22 secured to the forward end 4ofthe engine. These are provided with suitable; ways 33 within which thepins 21 are adjusted. The adjusting is effected by a rock shaft 24carried by the bracket 22 disposed transversely of the propeller shaftbeneath the yoke 20.

' Upwardly extending arms.25 are slotted at I, from this rock shaft.

- I Each rock'shaft arm 28 is operated by a FF '26 to receive the pins27 on the oppositeends of the yoke 20; Arms 28 extend down "controllever 29 in the cockpit, the same I having downwardly depending arm 30connected by the cont'rolrod 31 to the arin 28 -(see Figs. III and V).The, control lever 29 is pivoted to the segmentgplate 34 on the fulcrum32. .The' segment 34 'is secured to a frame piece 35 of the fuselage.The segment is provided with internal gear teeth 36 whieh are engaged bya latch 37 having double teeth 38, '38 spaced to engage one notch andride upon a tooth at the opposite side, making the adjustment a half ofa tooth The latch is controlled bythe rod 39 from the push button 40 atthe top of the control lever 29. (see Fig. V).

Because '-of the danger of speeding. an airplane engine, there isassociated with the reverse lever in the cockpit a control for thethrottle when reversing the propeller. This consists of a lever 41fulcrumed at 42 on the, control segment and connected at 44 through thespecial rod 43 to the throttle control [45. The throttle control rod isdivided and provided with extensible spring means WhlCl'l come into playwhen the propeller control yis off the neutral. A eompress1on coilspring 46 en- '55 gages a head 47 on the upper portion of the rod, and asleeve 48 is earned by the lower portion of the rod, and has a capretaining the spring in its'operative position. The lengthening of thethrottle control rod is thus permitted when the propeller. control leveris off the neutral and 1s locked; when the'propeller is at neutraL. Theaux .iliary lever 41 is disposed at" the side of f 'the propellercontrol lever 29 and is provided with a cam slot which iscngaged by'aroller '51, the. cam being so sl W ed that the lever 41 throttles theengine en the lever'29 is moved to the neutral position, as will clearlvappear. from an inspection of Fig. I throttle, the engine at this itatethe manipulation.

- With this improved construction it is possible for the pilot of an airlane to manipulate and completely and eEectively point to facilcontrolthe angle of the propeller blades. Asthe airplane ascends into higheratmosphere it isdesirable to turn the blades to cause them to advancemore stro n ly and thus most effectively advance the airplane. Theblades revolve much more freely in the attenuated air of the higheraltitudes.

This adjustment enables the full ower of the engine to be utilized. Thisadjustmentof the angle of the propeller blades is also of greatadvantage at the .take oil, as it enables the adjustment to be'maderecisely" to the-power of the engine and t e most powerful result isattalned. I

The reversing feature of the propeller enables the aviator tosubstantially stop his ane in mid-air. This would be a matter of greatadvantage in' combat, as it would give the pilot such control of hismachine as to mmimlze the attack of an enemy.

However, this matter of the reverse of a It' is important to propellerin the air is only of special consequence, Whereas the proper reversinof the propeller in landing after every is of the very highestconsequence, as it enablesthe machine to land safely and in a very shortspace. Machines have been landed and stopped upon the ground con-'siderably within one hundred feet, depending upon the power of theengine and the relative. weight of the plane, the landing spacerequired. for an airplane can be thus rection of revolution is notchanged. It is thus possible to put brakes upon the airplane when it isa little distance above the ground and it will drop immediately to theground and the reversal of the propeller acts as a powerful brake,"stopping the machine within a comparatively few feet. This is a matterof very great consequence-in avoid ing accidents in,landing and alsoinsuring landing within a limited area, and makes it practical toutilize Small landing fields.

By use of our invention it will thus be ob served that it is possiblefor the pilot' of an airplane tocompletely and instantly regulate theaction of the propeller and thereby the whole machine. This is a matterof importance in the take of". It

is also a matter of high consequence when the machine reaches hi haltitudes where the. air is attenuated. he reversal of the propeller bysubstantially the same means enables the pilot to completely control hisWe have provided simple and effective means which we desire to claimspecifically herein, but it isi-also desired to claim. the broadcombination in an airplane of thedevices and means that we haveproduced, as pointed out in the appended claims.

Having thus described our invention what we claimv as new and desire tosecure by Letters Patent/is:

1. The combination of an airplane, a proeller shaft therefor, apropeller hub with ateral sleeves, adjustable propeller bladessupportedin the said sleeves, a yoke transyerse to the said sleeves onthe said propeller hub, sup orting'pins from the said yoke to'the saihub parallel td the axis of said hub, anaxially adjustable ing carriedby said ins and revoluble wit said hub, pivoted llIlk connections fromthe said ring to said adjustable propeller blade, one

" above and the other below the said. sleeves,

an adjustable bearing yoke carried by the engine and embracing saidadjustable ring and constituting a bearing support therefor, ball thrustbearings between said adjustable yoke and ring, ins carried by saidadjustable yoke and dis osed parallel to the propeller shaft, brac etson the front nectionstherefrom to said rock I auxiliary leverpivoted tosaid locksegment; and disposed improximity'to the ad'usting end of theengine with hearing ways for .said pins, a" rock shaft carried by saidbrackets, arms on. saidv rock shaft slotted.

to engage pins on the end of said adjustable yoke, an adjusting leverwith lock segment in the cockpit of said airplane, con

shaft, an

lever, a cam slot in saidv lever, a 1'0 or on said adjusting leverengagingsaid cam'slot,

extensible connections from said lever to the throttle of'the e,; th'edcam being formed to actuate the throttle and to throttle the enginewhen the adjusting lever is at neutral, all coacting substantially asdescribed for the purpose specified.

2. The combination of an airplane, a propeller shaft therefor, aropeller hub with lateral sleeves,.adjustab e propeller blades supportedin the said sleeves, ayoke transverse to the said sleeves on the saidpro peller hub, supporting pins from 'the said yoke to .the said hubparallel to the axis of said hub, anaxially adjustable ring carried bysaid pins and revo-luble with said hub, pivoted link connections .fromthe said ring to said adjustable propeller blade, one

above and the other below the said sleeves,

an adjustable bearing yokecarried by the engine and embracing saidadjustable ring and constituting a bearing support there-- for, ballthrust bearings between said adjustable yoke and ring, pins carried bysaid adjustable yoke and disposed parallel to the propeller shaft,brackets on the front end of the engine with bearing ways for said pins,21 rock shaft carried by'sald brackets,

arms on said rock shaft slotted to engage pins on the end of saidadjustable yoke, an adjusting lever with lock segment in the cockpit ofsaid airplane, connections therefrom to said rock shaft, all coactingsubstantially as' described for the purpose specified.

3. The combination of an airplane, a propeller therefor with reversibblades, a control'lever in the cockpit of the airplane, connectionsfromsaid control lever tolsaid reversible blade, an auxiliary lever disposedin operative relation to said control lever,.having a cam therein, a pinon the control lever operating on said cam, connections from the saidauxiliary lever to the throttle of the engine, said cam being formed anddisposed to automatically throttle the engine when the control lever ismoved to neutral, coacting as specified.

4. The combination of an airplane, a propeller shaft therefor, apropeller hub with lateral sleeves. adjustable propeller bladessupported in the said'sleeves, a yoke transverse to the said sleeves onthe said propeller hub, supporting pins from' the said e propeller yoketo the said hub parallel to the axis of said hub, an axially adjustablering carried by saidpins and revoluble with said hub, pivoted linkconnections from the said ringto said adjustable propeller blade, oneabove and the other below the sald sleeves, an adjustable bearing yokecarried by the engine and embracing said adjustable ring andconstituting abearing support therefor, ballthrust bearings between saidadjustable yoke and ring, ins carried by said adjustable yoke and 1sosed parallel to the propeller" shaft, brac ets on the front end. of theengine with bearing waysfor j id pins, and means forfadj-usting saidbearing yoke. v 5. T e combination of an airplane, a

propeller shaft therefor, a propeller hub with lateral sleeves,adjustable propeller blades supported in the said sleeves, a yoketransverse to? the said, sleeves on the said propeller hub, supportingpins from the said. yoke to the said hub parallel to the axis of'saidhub, an axially adjustable ring carried by said pins I and revoluble.with said hub, pivoted link connections froin the 'said ring-to saidadjustable propeller blade,

'f one above and the other below the said sleeves, an adjustable bearingyoke carried ,by the engine and embracing said adjustable ring andconstituting a bearing support propeller shafttherefor, a propellerhu'bther'efor, ball thrust bearings between said adjustable yoke andring, and means for supporting and adjusting said bearing yoke.

The combination of an airplane, a

with lateral sleeves, adjustable propellor blades suppor'ted in the Saidsleeves, a. yoke. transverse to the said'sleeves on the said pro ellerhub, supporting pins from the sai yoke to the said hub parallel to the.axis of saidhub, an axially adjustable rin carried by said ins andrevoluble with .sai hub, pivoted lin connections from the said ring tosaid adjustable propeller blade, one above and the other below the saidsleeves, an 'adjustableybearing yoke carried by the engine and embracingsaid adjustable ring and constituting a bearing support therefor, pinscarried by said adjustable yoke and disposed parallel "to theropellershaft, brackets on the front en the engine with bearing ways forsaid pins, and means for adjusting" said bearing yoke.

7. Thecombination of an airplane, a proeller shaft therefor, a propellerhubwith ateral sleeves, adjustable propeller blades supported in thesaid sleeves, a yoke transverse to the said sleeves on the. said propeller hub, sup ortingpins from the said yoke to the sai .hub parallelto the axis of the said hub, an iaxi'ally adjustable ring carried bysaid inssand revoluble with & 'connection's from the said hub, pivoted1i propeller shaft therefor, a

said ring to said adjustable propeller blade,

one above and the other below the said sleeves, an adjustablebearingyoke carried by the engine and embracing said adjustable ringand, constituting a bearing support therefor, and means for supportingand adjusting said bearing yoke. v 8. The combination of an airplane, aropellerhub with lateral sleeves, *adjustafiile propeller bladessupported'in the said sleeves, an axially adjustable ring carried bysaid hub, pivoted link connections from the said ring to said adjustablepropeller blade, one above and the other below the said sleeves, anadjustable bearing yoke carried by the engine. and embracingsaldadjustable'ring and constituting a bearing support therefor, pinscarried by said adjustable yoke and disposed ally adjustable ringcarried by said hub, pivoted link connections from the said ring to saidadjustable ropeller blade, one above and the other be ow the saidsleeves, an adjustable bearing yoke carried by the engine and embracingsaid adjustable ring I andconstituting a bearing support therefor, pinscarried b said adjustable yoke and disposed paral e1 to vthe propellershaft, brackets on the front end of the engine .withbearing ways forsaid pins, a rock shaft carried by. said brackets, and arms on said'rockshaft slotted to engage pins on the end of said adjustable yoke.

our hands and seals.

SETH HART.

In witness-whereoflwe have hereunto set v [1,. 5.] ROBERT I. EUSTIS;[Ls];

